US20040093872A1 - Internally coolable screw - Google Patents
Internally coolable screw Download PDFInfo
- Publication number
- US20040093872A1 US20040093872A1 US10/640,268 US64026803A US2004093872A1 US 20040093872 A1 US20040093872 A1 US 20040093872A1 US 64026803 A US64026803 A US 64026803A US 2004093872 A1 US2004093872 A1 US 2004093872A1
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- US
- United States
- Prior art keywords
- screw
- combustion
- shank
- head
- coolant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002826 coolant Substances 0.000 claims abstract description 76
- 238000002485 combustion reaction Methods 0.000 claims description 34
- 238000001816 cooling Methods 0.000 abstract description 21
- 239000007789 gas Substances 0.000 description 13
- 238000005266 casting Methods 0.000 description 5
- 239000012809 cooling fluid Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000003313 weakening effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000036540 impulse transmission Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B33/00—Features common to bolt and nut
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
- F16B35/041—Specially-shaped shafts
- F16B35/044—Specially-shaped ends
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
- F16B35/06—Specially-shaped heads
Definitions
- the invention generally relates to a screw which can be internally cooled by a flowing coolant.
- Screws subjected to high mechanical and thermal loads are used, for example, in gas turbine construction.
- An example of application is the fastening of a combustion-chamber inner lining to a wall of a combustion chamber.
- the screws can be designed to be coolable.
- the fastening screw has, for example, an axial bore through which a cooling fluid, in particular cooling air, is directed into the combustion chamber from the outside of the latter.
- the cooling fluid mixes with the fuel gases in the combustion chamber.
- the loss of efficiency associated therewith is tolerated in order to ensure sufficient strength of the fastening screws by means of the cooling.
- ensuring sufficient mechanical loading capacity of the fastening screws means a considerable coolant requirement.
- An object of an embodiment of the invention is to specify a screw which can be internally cooled by a flowing coolant.
- a further object of an embodiment of the invention is to specify a screw which has an especially low coolant requirement.
- An object may be achieved by a screw having a head, a shank, and a coolant passage having an inflow opening and an outflow opening.
- the coolant passage does not pass axially through the entire head.
- the screw has “closed cooling”.
- a coolant inlet or outlet is arranged in each case on both end faces of the screw, i.e. both on the end face of the shank and on the top surface of the head. At least one coolant inlet or outlet is arranged laterally, i.e. between the top surface of the head and the end face of the shank.
- a coolant flow directed radially toward the longitudinal axis of the screw can therefore be produced—in the case of a lateral coolant inlet. Due to this radial coolant flow, the screw is cooled from outside by the same coolant which cools it from inside. This makes possible especially effective use of coolant, i.e. very effective utilization of the heat capacity of the coolant, and thus especially economical use of coolant.
- the temperature difference between the coolant and the screw to be cooled is utilized to an especially high degree.
- the coolant outlet is arranged laterally on the screw in such a way that the coolant flowing out of the screw flows in the axial direction along the shank.
- the coolant outlet opening is advantageously arranged as far as possible directly next to the head or on the head itself or in the transition region between head and shank.
- the coolant flows out of the coolant outlet opening axially in the direction of the end face of the shank.
- the coolant inlet opening is preferably located on the end face of the shank, i.e. on the shank end. The coolant inflow direction is thus opposed to the coolant outflow direction.
- a plurality of outlet openings are preferably arranged on the shank circumference and/or on the head.
- the uniformly distributed outlet openings have the advantage that asymmetrical weakening of the cross section of the shank and thus an unnecessary reduction in the mechanical loading capacity are avoided.
- the coolant outlet opening or openings is/are preferably arranged in a screw collar defining the shank toward the head as a thickened region of the shank.
- the head of the screw is internally cooled, the direction of flow of the coolant preferably being deflected in the head, i.e. the latter has a “deflecting region”.
- a coolant inlet or outlet opening is preferably not provided on the top surface or end face of the head.
- processes, for example chemical reactions, which take place in the space bordering the end face of the head are not affected by coolant or other fluid flowing into or out of this space.
- the coolant flowing out of the screw laterally in the region of the shank, the head and/or the screw collar is advantageously passed on in a specific manner and/or is advantageously conducted in a closed coolant circuit.
- a coolant inlet opening arranged axially in the shank end is especially suitable for a specific cooling feed or return.
- the coolant can in this case flow into the coolant passage, which to begin with runs axially in the shank, without deflection and thus virtually without pressure loss.
- a feed line can be connected, for example screwed, in a simple manner to the coolant inlet opening arranged on the shank end.
- Specific cooling of the head is especially important for the safety of the screwed connection during high thermal stressing.
- the entire head should be cooled as uniformly as possible. This is preferably achieved by the fact that the coolant flowing through the shank into the screw flows in a straight line at least up to the screw collar, in particular up to the head, and is not deflected until in the head, the coolant being split up in the deflecting region into a plurality of coolant partial flows.
- the individual sectional passages are distributed at least approximately uniformly, in particular in a rotationally symmetrical manner, in the head of the screw, also in the screw collar if need be.
- the closed internally cooled screw is especially suitable for fastening a combustion-chamber inner lining to a combustion-chamber wall of a gas turbine.
- FIGS. 1 a, b show an internally coolable screw and a cutaway detail of a coolant passage of the internally coolable screw
- FIG. 2 shows the internally coolable screw according to FIG. 1 with an associated bush
- FIG. 3 shows a gas turbine with a gas-turbine combustion chamber having a screw according to FIGS. 1 and 2.
- FIG. 1 a shows an internally coolable screw 1 , the coolant passage or cooling passage 2 of which is shown as a cutaway detail in FIG. 1 b .
- the screw 1 has a shank 3 and a head 4 and extends along an axis or axis of symmetry A from a top surface 5 , lying at the bottom in the representation, of the head 4 up to a shank end 6 .
- the shank 3 with a shank circumference 7 , has a thread 8 and a screw collar 9 of thickened design defining the shank 3 toward the head 4 .
- the head 4 On its top surface 5 , the head 4 has a hexagonal actuating opening 10 for a hexagon socket key.
- a coolant or cooling fluid F flows axially at the shank end 6 in inflow direction R 1 into an inflow opening 6 a of the screw 1 and discharges from the latter at three coolant-outflow openings or outflow openings 12 in outflow direction R 2 , which is opposed to the inflow direction R 1 .
- the cooling passage 2 runs first of all coaxially in the shank 3 and, in the head 4 , assumes the course indicated by broken lines in FIG. 1 a and shown in detail in FIG. 1 b .
- the cooling passage 2 widens close above the actuating opening 10 , as a result of which an impingement-cooling effect is produced in this region.
- the region of the cooling passage 2 in the head 4 is referred to as deflecting region 13 .
- the cooling passage 2 splits into three curved sectional passages 14 .
- the sectional passages or branches 14 have a uniform cross section and run inside the head 4 as far as close to the top surface 5 .
- the sectional passages 14 branch in a smoothly blended manner into twice the number of fine passages 15 .
- the six fine passages 15 run close to the surface of the head 4 before they are blended smoothly inward, i.e. in the direction of the axis A, and two fine passages 15 each are combined to form one sectional passage 14 .
- the coolant F discharges from the screw 1 through the outflow openings 12 arranged in a rotationally symmetrical manner in the screw collar 9 .
- the head 4 of the screw 1 is thus cooled intensively without coolant F flowing out in the direction of the top surface 5 .
- a sealing ring 17 can be put onto the inside 16 of the head 4 .
- the outflow openings 12 are open radially outward, i.e. toward the sealing ring 17 put onto the screw collar 9 .
- the screw 1 is made of a cast material.
- the shape of the cooling passage 2 is selected in such a way that the screw 1 , including the entire cooling passage 2 , can be produced by a casting process. Further processing steps, in particular machining steps, such as drilling, are not necessary for producing the cooling passage 2 , including the sectional passages 14 and the fine passages 15 .
- the casting process works without the use of “lost inserts”.
- the screw 1 with the cooling passage 2 is formed in such a way that, with an undercut being avoided, the casting process can be carried out using a plurality of mask elements.
- first mask element to be positioned in a casting mold, in which first mask element a second mask element is guided like a slide in a displaceable manner. After the casting, the mask elements can easily be removed and can therefore be reused.
- the screw 1 can be screwed together with a bush 18 .
- the bush 18 has an external thread 19 designed as a left-hand thread and also an internal thread 20 , which, in the same way as the thread 8 of the screw 1 , is designed as a right-hand thread and into which the screw 1 can be screwed.
- the bush 18 is screwed from outside into a wall (not shown here) of a combustion chamber of a gas turbine. A combustion-chamber inner lining is fastened with the screw 1 to the wall of the combustion chamber.
- the screw 1 is counterscrewed together with the bush 18 .
- the internal thread 20 has an oval cross-sectional region 21 .
- the screw 1 is secured by clamping the thread 8 in the oval cross-sectional region 21 without further securing elements.
- the closed internally cooled screw 1 therefore contributes to the especially effective utilization of the coolant F and at the same time, by increasing the combustion-air temperature, helps to achieve a high efficiency of the gas turbine.
- a gas turbine 22 is schematically shown in cross section in FIG. 3.
- the gas turbine 22 has a compressor 23 for combustion air, a gas-turbine combustion chamber or combustion chamber 24 , and a turbine 25 for driving the compressor 23 and a generator (not shown) or driven machine.
- the turbine 25 and the compressor 23 are arranged on a common turbine shaft 26 , which is also referred to as turbine rotor and to which the generator or the driven machine is also connected, and which is rotatably mounted about its center axis 26 a.
- the combustion chamber 24 is fitted with a number of burners 33 for burning a liquid or gaseous fuel.
- a combustion-chamber wall 27 is lined with a combustion-chamber inner lining 28 .
- the turbine 25 has a number of rotatable moving blades 29 connected to the turbine shaft 26 .
- the moving blades 29 are arranged in a ring shape on the turbine shaft 26 and thus form a number of moving blade rows.
- the turbine 25 comprises a number of fixed guide blades 30 , which are likewise fastened in a ring shape to an internal casing 31 of the turbine 25 while forming guide blade rows.
- the moving blades 29 thus serve to drive the turbine shaft 26 by impulse transmission of the working medium M flowing through the turbine 25 .
- the guide blades 30 serve to guide the flow of the working medium M between in each case two moving blade rows or moving blade rings following one another as viewed in the direction of flow of the working medium M.
- a successive pair consisting of a ring of guide blades 30 or a guide blade row and of a ring of moving blades 29 or a moving blade row is referred to as a turbine stage.
- the gas turbine 22 is operated at a high temperature of the working medium M.
- the working medium M discharges from the combustion chamber 24 at a temperature of about 1200 to 1300° C.
- the compressed combustion air fed for the combustion is preheated in a shell space 23 , which is formed between the inner wall 27 of the combustion chamber 24 and the combustion-chamber inner lining 28 , before entry to the burner 23 .
- the inner wall 27 of the combustion chamber 24 is cooled at the same time.
- the screw 1 which holds the combustion-chamber inner lining 28 on the inner wall 27 of the combustion chamber 24 , is subjected to high mechanical and thermal loads under these operating conditions.
- the head 4 of the screw 1 projects into the combustion chamber 24 .
- the highly efficient cooling of the screw 1 in particular of the head 4 , provides for a high strength of the screw 1 with sufficient safety reserves under all operating conditions.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present application hereby claims priority under 35 U.S.C. §119 on European patent application number EP 02018492.5 filed Aug. 16, 2002, the entire contents of which are hereby incorporated herein by reference.
- The invention generally relates to a screw which can be internally cooled by a flowing coolant.
- Screws subjected to high mechanical and thermal loads are used, for example, in gas turbine construction. An example of application is the fastening of a combustion-chamber inner lining to a wall of a combustion chamber.
- It is normally attempted to operate a gas turbine with as high a temperature as possible in the combustion chamber in order to achieve a high efficiency. Gas temperatures of 1200° C. to 1300° C. are typically achieved at the outlet of the combustion chamber. The combustion-chamber inner lining is often fastened to the combustion-chamber wall with screws inserted from the inside, i.e. from the combustion chamber. The head of the screws is therefore directly exposed to the fuel gas in the combustion chamber. If the screw or a part of the screw, in particular the screw head, due to a failure of said screw, gets into the combustion chamber and is entrained by the gas flow, serious damage to the downstream turbine is the result.
- In order to reliably prevent failure of the fastening screws arranged in the combustion chamber, the screws can be designed to be coolable. To this end, the fastening screw has, for example, an axial bore through which a cooling fluid, in particular cooling air, is directed into the combustion chamber from the outside of the latter. The cooling fluid mixes with the fuel gases in the combustion chamber. As a result, the temperature in the combustion chamber is undesirably reduced. The loss of efficiency associated therewith is tolerated in order to ensure sufficient strength of the fastening screws by means of the cooling. However, ensuring sufficient mechanical loading capacity of the fastening screws means a considerable coolant requirement.
- An object of an embodiment of the invention is to specify a screw which can be internally cooled by a flowing coolant. A further object of an embodiment of the invention is to specify a screw which has an especially low coolant requirement.
- An object may be achieved by a screw having a head, a shank, and a coolant passage having an inflow opening and an outflow opening. The coolant passage does not pass axially through the entire head. The screw has “closed cooling”.
- It is out of the question for a coolant inlet or outlet to be arranged in each case on both end faces of the screw, i.e. both on the end face of the shank and on the top surface of the head. At least one coolant inlet or outlet is arranged laterally, i.e. between the top surface of the head and the end face of the shank. In particular in cases in which an exclusively axial coolant inlet or outlet is not possible or is not desirable from the processing point of view, a coolant flow directed radially toward the longitudinal axis of the screw can therefore be produced—in the case of a lateral coolant inlet. Due to this radial coolant flow, the screw is cooled from outside by the same coolant which cools it from inside. This makes possible especially effective use of coolant, i.e. very effective utilization of the heat capacity of the coolant, and thus especially economical use of coolant. The temperature difference between the coolant and the screw to be cooled is utilized to an especially high degree.
- According to a preferred configuration, the coolant outlet is arranged laterally on the screw in such a way that the coolant flowing out of the screw flows in the axial direction along the shank. In this way, in addition to the inner cooling of the screw, especially effective cooling of the outer surface of the screw is also ensured. In order to cool the shank over its entire length not only from inside but also from outside, the coolant outlet opening is advantageously arranged as far as possible directly next to the head or on the head itself or in the transition region between head and shank. The coolant flows out of the coolant outlet opening axially in the direction of the end face of the shank. On the other hand, the coolant inlet opening is preferably located on the end face of the shank, i.e. on the shank end. The coolant inflow direction is thus opposed to the coolant outflow direction.
- In order to cool the entire circumference of the shank as uniformly as possible from outside, a plurality of outlet openings, preferably distributed at least approximately in a rotationally symmetrical manner about the axis of the screw, are preferably arranged on the shank circumference and/or on the head. In addition, the uniformly distributed outlet openings have the advantage that asymmetrical weakening of the cross section of the shank and thus an unnecessary reduction in the mechanical loading capacity are avoided. The coolant outlet opening or openings is/are preferably arranged in a screw collar defining the shank toward the head as a thickened region of the shank. By the arrangement of the coolant outlet openings in the screw collar, weakening of the cross section of the shank on account of the coolant outlet openings is avoided. Furthermore, the screw collar can serve to deflect the direction of flow of the coolant.
- According to a preferred configuration, the head of the screw is internally cooled, the direction of flow of the coolant preferably being deflected in the head, i.e. the latter has a “deflecting region”. A coolant inlet or outlet opening is preferably not provided on the top surface or end face of the head. In this way, processes, for example chemical reactions, which take place in the space bordering the end face of the head are not affected by coolant or other fluid flowing into or out of this space. On the other hand, the coolant flowing out of the screw laterally in the region of the shank, the head and/or the screw collar is advantageously passed on in a specific manner and/or is advantageously conducted in a closed coolant circuit. In this case, a coolant inlet opening arranged axially in the shank end is especially suitable for a specific cooling feed or return. The coolant can in this case flow into the coolant passage, which to begin with runs axially in the shank, without deflection and thus virtually without pressure loss. Furthermore, a feed line can be connected, for example screwed, in a simple manner to the coolant inlet opening arranged on the shank end.
- Specific cooling of the head is especially important for the safety of the screwed connection during high thermal stressing. In this case, the entire head should be cooled as uniformly as possible. This is preferably achieved by the fact that the coolant flowing through the shank into the screw flows in a straight line at least up to the screw collar, in particular up to the head, and is not deflected until in the head, the coolant being split up in the deflecting region into a plurality of coolant partial flows. In this case, the individual sectional passages are distributed at least approximately uniformly, in particular in a rotationally symmetrical manner, in the head of the screw, also in the screw collar if need be.
- The closed internally cooled screw is especially suitable for fastening a combustion-chamber inner lining to a combustion-chamber wall of a gas turbine.
- The advantages of an embodiment of the invention lie in particular in the fact that, by avoiding a coolant flow which passes axially through the entire screw, firstly especially effective utilization of the coolant can be achieved, in particular by coolant which also flows on the outer surface of the screw. Secondly, this avoids an undesirable inflow and/or outflow of coolant into or out of the screw, as a result of which an unintentional direct effect of coolant on a space arranged axially to the screw is ruled out.
- An exemplary embodiment of the invention is explained in more detail below with reference to the drawings, in which:
- FIGS. 1a, b show an internally coolable screw and a cutaway detail of a coolant passage of the internally coolable screw,
- FIG. 2 shows the internally coolable screw according to FIG. 1 with an associated bush,
- FIG. 3 shows a gas turbine with a gas-turbine combustion chamber having a screw according to FIGS. 1 and 2.
- Parts corresponding to one another are provided with the same designations in all the figures.
- FIG. 1a shows an internally
coolable screw 1, the coolant passage orcooling passage 2 of which is shown as a cutaway detail in FIG. 1b. Thescrew 1 has a shank 3 and a head 4 and extends along an axis or axis of symmetry A from a top surface 5, lying at the bottom in the representation, of the head 4 up to ashank end 6. The shank 3, with ashank circumference 7, has athread 8 and a screw collar 9 of thickened design defining the shank 3 toward the head 4. On its top surface 5, the head 4 has ahexagonal actuating opening 10 for a hexagon socket key. - A coolant or cooling fluid F flows axially at the
shank end 6 in inflow direction R1 into aninflow opening 6 a of thescrew 1 and discharges from the latter at three coolant-outflow openings oroutflow openings 12 in outflow direction R2, which is opposed to the inflow direction R1. Thecooling passage 2 runs first of all coaxially in the shank 3 and, in the head 4, assumes the course indicated by broken lines in FIG. 1a and shown in detail in FIG. 1b. Thecooling passage 2 widens close above theactuating opening 10, as a result of which an impingement-cooling effect is produced in this region. The region of thecooling passage 2 in the head 4 is referred to as deflectingregion 13. - After it has widened, the
cooling passage 2 splits into three curvedsectional passages 14. The sectional passages orbranches 14 have a uniform cross section and run inside the head 4 as far as close to the top surface 5. There, thesectional passages 14 branch in a smoothly blended manner into twice the number offine passages 15. The sixfine passages 15 run close to the surface of the head 4 before they are blended smoothly inward, i.e. in the direction of the axis A, and twofine passages 15 each are combined to form onesectional passage 14. - Via the three
sectional passages 14 thus combined in the vicinity of the shank 3, the coolant F discharges from thescrew 1 through theoutflow openings 12 arranged in a rotationally symmetrical manner in the screw collar 9. The head 4 of thescrew 1 is thus cooled intensively without coolant F flowing out in the direction of the top surface 5. A sealingring 17 can be put onto the inside 16 of the head 4. Theoutflow openings 12 are open radially outward, i.e. toward the sealingring 17 put onto the screw collar 9. - The
screw 1 is made of a cast material. The shape of thecooling passage 2 is selected in such a way that thescrew 1, including theentire cooling passage 2, can be produced by a casting process. Further processing steps, in particular machining steps, such as drilling, are not necessary for producing thecooling passage 2, including thesectional passages 14 and thefine passages 15. The casting process works without the use of “lost inserts”. To this end, thescrew 1 with thecooling passage 2 is formed in such a way that, with an undercut being avoided, the casting process can be carried out using a plurality of mask elements. In this case, provision is made for a first mask element to be positioned in a casting mold, in which first mask element a second mask element is guided like a slide in a displaceable manner. After the casting, the mask elements can easily be removed and can therefore be reused. - As FIG. 2 shows, the
screw 1 can be screwed together with abush 18. Thebush 18 has anexternal thread 19 designed as a left-hand thread and also aninternal thread 20, which, in the same way as thethread 8 of thescrew 1, is designed as a right-hand thread and into which thescrew 1 can be screwed. Thebush 18 is screwed from outside into a wall (not shown here) of a combustion chamber of a gas turbine. A combustion-chamber inner lining is fastened with thescrew 1 to the wall of the combustion chamber. Due to the design of theexternal thread 19 of thebush 18 as a left-hand thread and the design of theinternal thread 20 of thebush 18 and of thecorresponding thread 8 of thescrew 1 as a right-hand thread, thescrew 1 is counterscrewed together with thebush 18. As a safety feature to prevent loosening, theinternal thread 20 has an ovalcross-sectional region 21. Thescrew 1 is secured by clamping thethread 8 in the ovalcross-sectional region 21 without further securing elements. - Enclosed between the combustion-chamber wall, into which the
bush 18 is screwed, and the combustion-chamber inner lining, which is held by thescrew 1, is a space in which cooling air F flows, which is then used as preheated combustion air. The coolant F flowing out of thescrew 1 flows into this space. This coolant F, which has already been heated in thescrew 1, thus contributes to the increase in the temperature of the combustion air to be fed to the gas turbine and thus to the increase in efficiency. In contrast, in the case of open cooling of thescrew 1, i.e. in the case of a complete axial flow of the coolant F through theentire screw 1, the coolant F would pass directly into the combustion chamber, reduce the temperature there and thus reduce the efficiency. - The closed internally cooled
screw 1 therefore contributes to the especially effective utilization of the coolant F and at the same time, by increasing the combustion-air temperature, helps to achieve a high efficiency of the gas turbine. - A
gas turbine 22 is schematically shown in cross section in FIG. 3. Thegas turbine 22 has acompressor 23 for combustion air, a gas-turbine combustion chamber orcombustion chamber 24, and aturbine 25 for driving thecompressor 23 and a generator (not shown) or driven machine. To this end, theturbine 25 and thecompressor 23 are arranged on acommon turbine shaft 26, which is also referred to as turbine rotor and to which the generator or the driven machine is also connected, and which is rotatably mounted about itscenter axis 26 a. - The
combustion chamber 24 is fitted with a number ofburners 33 for burning a liquid or gaseous fuel. A combustion-chamber wall 27 is lined with a combustion-chamberinner lining 28. - The
turbine 25 has a number of rotatable movingblades 29 connected to theturbine shaft 26. The movingblades 29 are arranged in a ring shape on theturbine shaft 26 and thus form a number of moving blade rows. Furthermore, theturbine 25 comprises a number of fixedguide blades 30, which are likewise fastened in a ring shape to aninternal casing 31 of theturbine 25 while forming guide blade rows. The movingblades 29 thus serve to drive theturbine shaft 26 by impulse transmission of the working medium M flowing through theturbine 25. Theguide blades 30, on the other hand, serve to guide the flow of the working medium M between in each case two moving blade rows or moving blade rings following one another as viewed in the direction of flow of the working medium M. In this case, a successive pair consisting of a ring ofguide blades 30 or a guide blade row and of a ring of movingblades 29 or a moving blade row is referred to as a turbine stage. - In order to make possible a high efficiency of the
gas turbine 22, thegas turbine 22 is operated at a high temperature of the working medium M. The working medium M discharges from thecombustion chamber 24 at a temperature of about 1200 to 1300° C. The compressed combustion air fed for the combustion is preheated in ashell space 23, which is formed between theinner wall 27 of thecombustion chamber 24 and the combustion-chamberinner lining 28, before entry to theburner 23. As a result, theinner wall 27 of thecombustion chamber 24 is cooled at the same time. Thescrew 1, which holds the combustion-chamberinner lining 28 on theinner wall 27 of thecombustion chamber 24, is subjected to high mechanical and thermal loads under these operating conditions. The head 4 of thescrew 1 projects into thecombustion chamber 24. The highly efficient cooling of thescrew 1, in particular of the head 4, provides for a high strength of thescrew 1 with sufficient safety reserves under all operating conditions. - The invention being thus described, it will be obvious that the same may be varied in many ways. Such variations are not to be regarded as a departure from the spirit and scope of the invention, and all such modifications as would be obvious to one skilled in the art are intended to be included within the scope of the following claims.
Claims (29)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02018492A EP1389690B1 (en) | 2002-08-16 | 2002-08-16 | Screw interiorly cooled |
EP02018492.5 | 2002-08-16 |
Publications (2)
Publication Number | Publication Date |
---|---|
US20040093872A1 true US20040093872A1 (en) | 2004-05-20 |
US6941758B2 US6941758B2 (en) | 2005-09-13 |
Family
ID=30470280
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/640,268 Expired - Fee Related US6941758B2 (en) | 2002-08-16 | 2003-08-14 | Internally coolable screw |
Country Status (6)
Country | Link |
---|---|
US (1) | US6941758B2 (en) |
EP (1) | EP1389690B1 (en) |
JP (1) | JP4539903B2 (en) |
CN (1) | CN100532946C (en) |
DE (1) | DE50209166D1 (en) |
ES (1) | ES2278847T3 (en) |
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EP1605209A1 (en) * | 2004-06-07 | 2005-12-14 | Siemens Aktiengesellschaft | Combustor with thermo-acoustic vibrations dampening device |
US20070062202A1 (en) * | 2005-09-16 | 2007-03-22 | Pratt & Whitney Canada Corp. | Cooled support boss for a combustor in a gas turbine engine |
EP1816357A1 (en) * | 2006-02-02 | 2007-08-08 | Siemens Aktiengesellschaft | Screw for a thermally charged environment |
US20110011095A1 (en) * | 2009-07-17 | 2011-01-20 | Ladd Scott A | Washer with cooling passage for a turbine engine combustor |
WO2015017180A1 (en) * | 2013-08-01 | 2015-02-05 | United Technologies Corporation | Attachment scheme for a ceramic bulkhead panel |
US20150260400A1 (en) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber shingle of a gas turbine |
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US20160313004A1 (en) * | 2015-04-23 | 2016-10-27 | United Technologies Corporation | Additive manufactured combustor heat shield |
US9518737B2 (en) | 2012-12-12 | 2016-12-13 | Rolls-Royce Plc | Combustion chamber with cooling passage in fastener arrangement joining inner and outer walls |
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US20190078789A1 (en) * | 2017-09-08 | 2019-03-14 | United Technologies Corporation | Cooling configuration for combustor attachment feature |
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EP1605209A1 (en) * | 2004-06-07 | 2005-12-14 | Siemens Aktiengesellschaft | Combustor with thermo-acoustic vibrations dampening device |
US20070062202A1 (en) * | 2005-09-16 | 2007-03-22 | Pratt & Whitney Canada Corp. | Cooled support boss for a combustor in a gas turbine engine |
US7559203B2 (en) | 2005-09-16 | 2009-07-14 | Pratt & Whitney Canada Corp. | Cooled support boss for a combustor in a gas turbine engine |
EP1816357A1 (en) * | 2006-02-02 | 2007-08-08 | Siemens Aktiengesellschaft | Screw for a thermally charged environment |
WO2007088098A1 (en) * | 2006-02-02 | 2007-08-09 | Siemens Aktiengesellschaft | Screw for use in thermally loaded surroundings |
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US20110011095A1 (en) * | 2009-07-17 | 2011-01-20 | Ladd Scott A | Washer with cooling passage for a turbine engine combustor |
US8800298B2 (en) * | 2009-07-17 | 2014-08-12 | United Technologies Corporation | Washer with cooling passage for a turbine engine combustor |
US9518737B2 (en) | 2012-12-12 | 2016-12-13 | Rolls-Royce Plc | Combustion chamber with cooling passage in fastener arrangement joining inner and outer walls |
US10422532B2 (en) | 2013-08-01 | 2019-09-24 | United Technologies Corporation | Attachment scheme for a ceramic bulkhead panel |
WO2015017180A1 (en) * | 2013-08-01 | 2015-02-05 | United Technologies Corporation | Attachment scheme for a ceramic bulkhead panel |
US20150260400A1 (en) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber shingle of a gas turbine |
US20160313004A1 (en) * | 2015-04-23 | 2016-10-27 | United Technologies Corporation | Additive manufactured combustor heat shield |
US10935240B2 (en) * | 2015-04-23 | 2021-03-02 | Raytheon Technologies Corporation | Additive manufactured combustor heat shield |
CN105507963A (en) * | 2015-12-23 | 2016-04-20 | 上海电气电站设备有限公司 | Cooling system for cooling bolt working at high temperature |
CN110494632A (en) * | 2017-03-30 | 2019-11-22 | 通用电气公司 | The machanical fastener of increasing material manufacturing with cooling channels |
US10533747B2 (en) | 2017-03-30 | 2020-01-14 | General Electric Company | Additively manufactured mechanical fastener with cooling fluid passageways |
WO2018182807A1 (en) * | 2017-03-30 | 2018-10-04 | General Electric Company | An additively manufactured mechanical fastener with cooling fluid passageways |
US20190078789A1 (en) * | 2017-09-08 | 2019-03-14 | United Technologies Corporation | Cooling configuration for combustor attachment feature |
US10619857B2 (en) * | 2017-09-08 | 2020-04-14 | United Technologies Corporation | Cooling configuration for combustor attachment feature |
US10670274B2 (en) | 2017-09-08 | 2020-06-02 | Raytheon Technologies Corporation | Cooling configurations for combustor attachment features |
US10670273B2 (en) | 2017-09-08 | 2020-06-02 | Raytheon Technologies Corporation | Cooling configurations for combustor attachment features |
US10670275B2 (en) | 2017-09-08 | 2020-06-02 | Raytheon Technologies Corporation | Cooling configurations for combustor attachment features |
Also Published As
Publication number | Publication date |
---|---|
EP1389690B1 (en) | 2007-01-03 |
JP4539903B2 (en) | 2010-09-08 |
EP1389690A1 (en) | 2004-02-18 |
JP2004076942A (en) | 2004-03-11 |
CN100532946C (en) | 2009-08-26 |
CN1485571A (en) | 2004-03-31 |
ES2278847T3 (en) | 2007-08-16 |
US6941758B2 (en) | 2005-09-13 |
DE50209166D1 (en) | 2007-02-15 |
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